GOE 180 (MVA H.26) AIRFOIL (goe180-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 180 (MVA H.26) AIRFOIL (goe180-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.04 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe180-il-1000000-n5.txt Download as CSV file: xf-goe180-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 180 (MVA H.26) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.4681 0.16367 0.16187 -0.0026 1.0000 0.0041
-13.750 -0.4578 0.15599 0.15420 -0.0055 1.0000 0.0042
-10.250 -0.6815 0.02293 0.02007 -0.0871 0.9951 0.0090
-10.000 -0.6537 0.01995 0.01676 -0.0895 0.9925 0.0096
-9.750 -0.6232 0.01799 0.01453 -0.0915 0.9893 0.0103
-9.500 -0.5910 0.01663 0.01295 -0.0933 0.9869 0.0109
-9.250 -0.5604 0.01631 0.01263 -0.0940 0.9829 0.0116
-8.750 -0.4990 0.01550 0.01173 -0.0956 0.9703 0.0130
-8.500 -0.4668 0.01442 0.01043 -0.0970 0.9612 0.0138
-8.250 -0.4310 0.01412 0.01008 -0.0988 0.9504 0.0144
-8.000 -0.3953 0.01434 0.01033 -0.1003 0.9396 0.0148
-7.750 -0.3621 0.01447 0.01044 -0.1013 0.9261 0.0153
-7.500 -0.3328 0.01437 0.01026 -0.1015 0.9121 0.0159
-7.250 -0.3056 0.01393 0.00966 -0.1015 0.9000 0.0166
-7.000 -0.2789 0.01334 0.00889 -0.1014 0.8900 0.0173
-6.750 -0.2517 0.01301 0.00841 -0.1012 0.8807 0.0178
-6.500 -0.2248 0.01256 0.00784 -0.1011 0.8718 0.0182
-6.250 -0.1975 0.01237 0.00759 -0.1010 0.8620 0.0186
-6.000 -0.1702 0.01224 0.00740 -0.1008 0.8508 0.0190
-5.750 -0.1428 0.01213 0.00723 -0.1007 0.8382 0.0194
-5.500 -0.1156 0.01197 0.00698 -0.1005 0.8240 0.0199
-5.250 -0.0886 0.01165 0.00654 -0.1003 0.8076 0.0204
-5.000 -0.0619 0.01141 0.00615 -0.1000 0.7871 0.0210
-4.750 -0.0352 0.01117 0.00575 -0.0996 0.7617 0.0216
-4.500 -0.0088 0.01093 0.00533 -0.0993 0.7325 0.0220
-4.250 0.0175 0.01078 0.00499 -0.0989 0.7000 0.0224
-4.000 0.0439 0.01074 0.00476 -0.0985 0.6649 0.0227
-3.750 0.0703 0.01070 0.00454 -0.0982 0.6267 0.0229
-3.500 0.0970 0.01060 0.00427 -0.0979 0.5956 0.0230
-3.250 0.1236 0.01004 0.00354 -0.0977 0.5722 0.0234
-3.000 0.1507 0.00973 0.00312 -0.0975 0.5535 0.0238
-2.750 0.1781 0.00951 0.00281 -0.0974 0.5376 0.0242
-2.500 0.2058 0.00934 0.00257 -0.0973 0.5261 0.0245
-2.250 0.2335 0.00922 0.00238 -0.0973 0.5145 0.0250
-2.000 0.2613 0.00911 0.00223 -0.0972 0.5036 0.0255
-1.750 0.2892 0.00900 0.00206 -0.0971 0.4948 0.0260
-1.500 0.3171 0.00891 0.00192 -0.0971 0.4864 0.0265
-1.250 0.3451 0.00883 0.00180 -0.0970 0.4792 0.0270
-1.000 0.3731 0.00877 0.00169 -0.0970 0.4716 0.0275
-0.750 0.4011 0.00872 0.00161 -0.0969 0.4636 0.0280
-0.500 0.4288 0.00871 0.00154 -0.0968 0.4526 0.0284
-0.250 0.4568 0.00868 0.00148 -0.0968 0.4443 0.0288
0.000 0.4847 0.00868 0.00144 -0.0967 0.4383 0.0291
0.250 0.5128 0.00865 0.00141 -0.0967 0.4332 0.0294
0.500 0.5407 0.00867 0.00139 -0.0967 0.4258 0.0296
0.750 0.5686 0.00867 0.00136 -0.0966 0.4177 0.0309
1.000 0.5964 0.00869 0.00135 -0.0966 0.4102 0.0332
1.250 0.6244 0.00870 0.00136 -0.0965 0.4051 0.0364
1.500 0.6522 0.00865 0.00140 -0.0965 0.3983 0.0761
1.750 0.6799 0.00866 0.00145 -0.0965 0.3910 0.1010
2.000 0.7077 0.00858 0.00152 -0.0965 0.3829 0.1723
2.250 0.7352 0.00849 0.00161 -0.0966 0.3740 0.2692
2.750 0.7851 0.00719 0.00190 -0.0957 0.3488 1.0000
3.000 0.8121 0.00737 0.00199 -0.0956 0.3299 1.0000
3.250 0.8381 0.00765 0.00213 -0.0953 0.2999 1.0000
3.500 0.8635 0.00802 0.00232 -0.0949 0.2664 1.0000
4.000 0.9159 0.00854 0.00267 -0.0944 0.2338 1.0000
4.250 0.9426 0.00874 0.00282 -0.0942 0.2253 1.0000
4.500 0.9693 0.00893 0.00298 -0.0940 0.2184 1.0000
4.750 0.9961 0.00910 0.00314 -0.0939 0.2127 1.0000
5.000 1.0230 0.00927 0.00330 -0.0937 0.2079 1.0000
5.250 1.0495 0.00946 0.00348 -0.0935 0.2027 1.0000
5.500 1.0762 0.00964 0.00365 -0.0933 0.1983 1.0000
5.750 1.1025 0.00984 0.00384 -0.0931 0.1901 1.0000
6.000 1.1283 0.01009 0.00405 -0.0928 0.1784 1.0000
6.250 1.1529 0.01048 0.00431 -0.0924 0.1552 1.0000
6.500 1.1760 0.01102 0.00469 -0.0917 0.1269 1.0000
6.750 1.2005 0.01139 0.00500 -0.0913 0.1159 1.0000
7.000 1.2253 0.01171 0.00530 -0.0909 0.1085 1.0000
7.250 1.2501 0.01202 0.00560 -0.0904 0.1019 1.0000
7.500 1.2745 0.01236 0.00592 -0.0900 0.0924 1.0000
8.000 1.3120 0.01417 0.00732 -0.0874 0.0268 1.0000
8.250 1.3336 0.01474 0.00785 -0.0865 0.0181 1.0000
8.500 1.3560 0.01520 0.00832 -0.0857 0.0144 1.0000
8.750 1.3781 0.01568 0.00881 -0.0849 0.0122 1.0000
9.000 1.4002 0.01613 0.00928 -0.0841 0.0108 1.0000
9.250 1.4221 0.01658 0.00977 -0.0832 0.0099 1.0000
9.500 1.4431 0.01708 0.01029 -0.0823 0.0090 1.0000
9.750 1.4629 0.01767 0.01092 -0.0812 0.0081 1.0000
10.000 1.4835 0.01815 0.01145 -0.0802 0.0077 1.0000
10.250 1.5033 0.01866 0.01201 -0.0791 0.0072 1.0000
10.500 1.5222 0.01922 0.01260 -0.0778 0.0067 1.0000
10.750 1.5398 0.01984 0.01326 -0.0764 0.0062 1.0000
11.000 1.5550 0.02059 0.01407 -0.0747 0.0058 1.0000
11.250 1.5697 0.02122 0.01476 -0.0728 0.0056 1.0000
11.500 1.5826 0.02188 0.01549 -0.0706 0.0054 1.0000
11.750 1.5946 0.02262 0.01629 -0.0684 0.0052 1.0000
12.000 1.6057 0.02342 0.01716 -0.0661 0.0050 1.0000
12.250 1.6159 0.02431 0.01812 -0.0639 0.0048 1.0000
12.500 1.6251 0.02530 0.01917 -0.0618 0.0046 1.0000
12.750 1.6333 0.02641 0.02036 -0.0597 0.0045 1.0000
13.000 1.6399 0.02770 0.02172 -0.0577 0.0043 1.0000
13.250 1.6445 0.02923 0.02334 -0.0557 0.0042 1.0000
13.500 1.6461 0.03112 0.02534 -0.0538 0.0040 1.0000
13.750 1.6499 0.03293 0.02724 -0.0523 0.0039 1.0000
14.000 1.6536 0.03486 0.02926 -0.0511 0.0039 1.0000
14.250 1.6566 0.03698 0.03148 -0.0501 0.0038 1.0000
14.500 1.6577 0.03941 0.03401 -0.0494 0.0037 1.0000
14.750 1.6575 0.04215 0.03686 -0.0490 0.0036 1.0000
15.000 1.6560 0.04520 0.04003 -0.0488 0.0035 1.0000
15.250 1.6527 0.04861 0.04355 -0.0490 0.0035 1.0000
15.500 1.6479 0.05235 0.04741 -0.0494 0.0034 1.0000
15.750 1.6414 0.05647 0.05165 -0.0501 0.0034 1.0000
16.000 1.6335 0.06085 0.05614 -0.0510 0.0033 1.0000
16.250 1.6239 0.06557 0.06098 -0.0520 0.0033 1.0000
16.500 1.6130 0.07058 0.06611 -0.0533 0.0032 1.0000
16.750 1.6003 0.07587 0.07152 -0.0547 0.0032 1.0000
17.000 1.5862 0.08148 0.07725 -0.0563 0.0032 1.0000
17.250 1.5716 0.08729 0.08318 -0.0580 0.0031 1.0000
17.500 1.5568 0.09319 0.08919 -0.0599 0.0031 1.0000
17.750 1.5400 0.09958 0.09570 -0.0621 0.0031 1.0000
18.000 1.5240 0.10597 0.10221 -0.0644 0.0031 1.0000
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